CN101410299A - System for deicing an air inlet cowl for a turbine engine - Google Patents
System for deicing an air inlet cowl for a turbine engine Download PDFInfo
- Publication number
- CN101410299A CN101410299A CN200780010760.9A CN200780010760A CN101410299A CN 101410299 A CN101410299 A CN 101410299A CN 200780010760 A CN200780010760 A CN 200780010760A CN 101410299 A CN101410299 A CN 101410299A
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- China
- Prior art keywords
- hot air
- branch
- linkwork
- removal system
- ice removal
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
Abstract
According to the invention, a scaled articulation device (27) is mounted on at least one (14) of the branches (14; 18, 9) of said hot-air circulation circuit in the form of a bracket so as to provide said bracket with capabilities of deforming about said articulation device (27).
Description
The present invention relates to deicing in particular for the air intake port cover of the turbine engine of aircraft.
Known (prevention forms frosting or eliminates the frosting that has formed) if desired, (bord d ' attaque) carries out deicing by using the pressurized heat air to reheat to the leading edge of the air intake port cover of these turbine engines, and this hot air is delivered to described leading edge from described turbine engine extraction and by the hot air circulate pipeline with it.Such hot air circulate pipeline comprises two rectangular branches in known manner, promptly, be connected to the transverse branch on the described turbine engine, and described relatively turbine engine is arranged laterad and be communicatively connected to vertical branch on the nozzle with described leading edge.
Yet the hot air that extracts from turbine engine has very high temperature, 500 ℃ rank for example, and have very high pressure, for example ranks of 10 to 20 crust.Cause thus in the temperature of described hot air and perhaps under the effect at the pressure of described hot air, the branch of described rectangular hot air circulate pipeline (making with steel pipe) stands big length variations.Therefore, by described transverse branch and vertically the rigidity right-angle structure that forms of branch the trend of distortion is arranged, and described hot air circulate pipeline is fastened to the device of described air intake port cover and stands very high stress from the device that turbine engine extracts the pressurized heat air, and this can make these devices damage or damage.
The objective of the invention is to remedy these defectives.
For this reason, according to the present invention, this system gives the leading edge deicing in particular for the air intake port cover of the turbine engine of aircraft, and described ice removal system comprises:
-be suitable for the pressurized heat blast injection to described hollow leading edge in-to-in nozzle;
-be installed on the hot-fluid producer of described turbine engine, be used for extracting the device of pressurized heat air;
-being used for carrying the hot air circulate pipeline of described pressurized heat air to described nozzle from described draw-out device, described hot air circulate pipeline comprises two rectangular branches, that is:
Transverse branch, its end is connected on the described draw-out device rigidly, and
Vertical branch, its described relatively turbine engine laterad arranges and its end is connected on the described nozzle, and
-securing device, it is arranged in described mentioned nozzle area, is used for described vertical branch is fastened to described air intake port cover,
It should be noted that at least one branch of described hot air circulate pipeline the leak free linkwork has been installed, be used to make described right-angle structure to be out of shape about described linkwork.
Like this, because the linkwork of sealing, when the length of described branch issues the growth degree when changing in the effect of the temperature of described hot air and/or pressure, the right-angle structure that is formed by described transverse branch and vertical branch also can be out of shape, the relative position that described branch is sent away them is adapted to their true length, and the securing device of described hot air circulate pipeline is not applied excessive stress.
The linkwork of sealing can be any known type, flexible sleeve for example, bellows etc.But each seals linkwork and is preferably the spherical coupling type.
In order to increase the possibility of described hot air circulate pipeline about described one or more linkwork distortion again, advantageously, each circulation line includes two spherical couplings that separate along the respective branches of described hot air pipeline.
Certainly, hot air circulate pipeline according to the present invention can be formed by independent pipeline.Yet owing to the temperature of the hot air that passes described pipeline is very high, so the heat of this pipeline radiation can damage some structure near described hot air circulate pipeline of described air intake port cover.In addition, for tangible security reason, if this pressurized heat escape of air or the fracture of described pipeline advantageously provide the protection near structure described.
Like this, according to the important feature of the present invention that can avoid defectives such as described leakage or fracture, in the transverse branch of described hot air circulate pipeline and vertically all similarly provide outer jointing jacket in the branch.
Like this; in an advantageous embodiments; each branch of the pivotally attached of described hot air circulate pipeline includes the hot air direct internal element that is equipped with described sealing linkwork; and around the protecting sleeve outer member of described inner member; described outer member is equipped with the linkwork of combination, and the described sealing linkwork of this linkwork and described inner member is arranged accordingly and implemented.
In this embodiment, in order to check and safeguard the sealing linkwork of described inner member, advantageously described protecting sleeve outer member is a detouchable.For this reason, at least one in the linkwork of the linkwork of this inner member and this outer member is knock-down spherical coupling type.For this purpose, can comprise the spherical coupling that cooperates with cylindrical surface about linkwork.
Experience shows that in order to obtain the desired result of the present invention, under most of situation, the described transverse branch of only hinged described hot air circulate pipeline is just much of that.
In first preferred embodiment according to ice removal system of the present invention:
Described vertical branch of-this hot air circulate pipeline comprises hot air direct internal element and around the protecting sleeve outer member of described inner member;
An element in these two composed components of the inner member of-described vertical branch and outer member is vertical rigidity, and another element in the described composed component comprises at least two parts nested each other and that can slide relative to one another in the leak free mode;
Two composed components of-described vertical branch connect each other at its place, two ends;
-in described mentioned nozzle area, these two composed components are connected on the described securing device together rigidly; And
-in described transverse branch zone; on the one hand; the described hot air direct internal element of the described hot air direct internal element of described vertical branch and transverse branch connects each other; and on the other hand, the described protecting sleeve outer member of described protecting sleeve outer member of described vertical branch and transverse branch connects equally each other.
Be indebted to such layout, stiffener in the described element of described vertical branch is as the pull bar of another element of comprising of these elements of described nested and slipper, so that in fact described vertical branch is limited by the prolongation under the temperature action of described stiffener at described hot air in the prolongation under the pressure effect of this hot air.Limited like this by described transverse branch and the vertically distortion of the right-angle structure that forms of branch, and thereby limited the rotation amplitude of the described linkwork of the inner member of described transverse branch and outer member.
In second preferred embodiment, adopted following prolongation limited features according to ice removal system of the present invention:
Vertical branch of-described hot air circulate pipeline comprises at least two sections, and they are the installation of front and back phase ground connection each other;
-each described section protecting sleeve outer member that comprises hot air direct internal element and center on described inner member;
An element in two composed components of-described section is vertical rigidity, and another element in the described composed component comprises at least two parts nested each other and that can slide relative to one another in the leak free mode;
-each two composed component of described section connect each other at its place, two ends;
Two sections of-described vertical branch are engaged with each other, so that connect their composed component respectively;
-in described mentioned nozzle area, two composed components of one section are connected on the described securing device together rigidly in two sections; And
-in described transverse branch zone; on the one hand; the described hot air direct internal element of described hot air direct internal element of another section of described section and described transverse branch connects each other; and on the other hand, the described protecting sleeve outer member of described another section and the protecting sleeve outer member of described transverse branch connect equally each other.
In addition, advantageously, in described mentioned nozzle area, described securing device comprises the separator that seals described hollow leading edge.
Accompanying drawing will make how easy to understand implements the present invention.In these accompanying drawings, the identical similar parts of label representative.
Fig. 1 is the signal exploded drawings of turbine engine, has wherein shown air intake port cover and ice removal system thereof.
Fig. 2 is the amplification part sectional view according to the described air intake port cover of the line II-II of Fig. 1.
Fig. 3 has schematically shown first embodiment of described ice removal system.
Fig. 4 has schematically shown the modification of the ice removal system of Fig. 3, and wherein the pressurized heat air is passing through described system.
Fig. 5 has schematically shown the cutaway view of pivotally attached embodiment of the ice removal system of Fig. 3.
Fig. 6 and Fig. 7 have schematically shown second embodiment and the 3rd embodiment of described ice removal system respectively.
Fig. 8 and Fig. 9 have schematically shown the cutaway view of two embodiment of pivotally attached of the ice removal system that is used for Fig. 6 and Fig. 7.
The double-current method driving engine 1 that schematically shows among Fig. 1 presents longitudinal axes L-L, and comprises hot air center producer 2, blowing engine 3 and compressor stage 4 in known manner.On driving engine 1, connect and fastening 5, two sides covers 6 of nozzle component and 7 and air intake port cover 8.
As by meaning demonstration illustrated in figures 1 and 2, air intake port cover 8 comprises that the in-to-in lateral longitudinal is to pipe fitting 9, be equipped with Connection Element 10 in its rear end of pointing to driving engine 1, and the front end place outfit nozzle 12 in it is contained in the hollow leading edge 11 of described air intake port cover.In addition, on the compressor stage 4 of driving engine 1, arranged pressurized heat air intlet 13, this air intlet 13 is connected on the inner transverse pipe fitting 14, and this pipe fitting 14 is connected on the vertical pipe fitting 18 that is contained between blowing engine 3 and the side cover 6 by bend pipe 15 and cooperation joint 16,17 itself.On the opposite of joint component 17, be equipped with vertical pipe fitting 18, this vertical pipe fitting 18 has acomplementary connector element 19 towards the joint component 10 of vertical pipe fitting 9.
Like this, when complementary on the one hand joint component 16 and 17, and complementary on the other hand joint component 10 and 19 is when being connected with each other, pipe fitting 9,14 and 18 constitute rectangular hot air circulate pipeline, and this hot air circulate pipeline comprises transverse branch 14 and vertical branch 9,18, flow through this hot air circulate pipeline by the hot air (for example having 500 ℃ temperature) that extracts from driving engine 1 at 13 places, and be transported to nozzle 12.This thus this pressurized heat air (dotted arrow 20) can be blown to the inside of leading edge 11, be used for deicing.In cover 8 outside face, be equipped with at least one hole 21, be used for discharging the free air (temperature is for example 200 ℃ in the case) of hot air that (arrow 22) passed through the inner loop of leading edge 11.
With the detailed demonstration of bigger ratio, this hollow leading edge 11 makes to form annular periphery compartment 24 in described leading edge 11 in the back by 23 sealings of inner annular separator as Fig. 2.The respective ends of nozzle 12 and vertical pipe fitting 9 is fastened on the inner separator 23, and the described nozzle that is arranged in the described ring chamber 24 sprays pressurized heat air 20 in this ring chamber 24.Hole 21 makes described ring chamber 24 be communicated with outside formation.
On the opposite of leading edge 11, air intake port cover 8 is by 25 sealings of inner annular separator, and the end that is supporting vertical pipe fitting 9 of joint component 10 freely passes this separator with sliding type.
Schematically show as Fig. 3, rectangular hot air circulate pipeline 9,14,18 thereby be fastened on the driving engine 1 by the import 13 of forced air and by separator 23 in their end, and support by separator 25 in the mode of sliding, and if desired, and other middle device 26 (articulated linkage that does not for example illustrate in addition) support.
According to the present invention, the linkwork 27 that comprises two spherical couplings 28,29 has been installed on transverse branch 14, these two spherical couplings 28,29 are separated from each other, and are installed in respectively on the two ends of inserting the pipe fitting section 30 in the pipe fitting 14. Spherical coupling 28,29 is cooperated with the spherical base 31,32 that is bound up on the pipe fitting 14 respectively.
Fig. 5 has shown an embodiment example of linkwork 27.In this example, seal bellows 33,34 is separately positioned between spherical coupling 28 and the pedestal 31 and is arranged between spherical coupling 29 and the pedestal 32.
Be readily appreciated that, with the mode that is equal to already described above, spherical coupling 28,29 can be bound up on the pipe fitting 14, and pedestal 31,32 can be bound up on the pipe fitting section 30.
As schematically showing among Fig. 4, when this hot air circulate pipeline of hot air process, this transverse branch 14 stands the extending transversely by the relative turbine engine 1 shown in the arrow 35, and vertically branch 9,18 stands by the extend longitudinally shown in the arrow 36.Because the existence of linkwork 27, by described branch 14 and 9,18 right-angle structure thereby the distortion that form, this has been avoided applying excessive stress on pressure inlets 13 and separator 23.
In the ice removal system that schematically shows by Fig. 6, seen element 4,9 again, 10,12 to 20,23 and 25 to 27, describe with reference to Fig. 3.Yet, in the system of Fig. 6:
-vertically pipe fitting 9 comprises with sleeve pipe and two nested each other element 9a of leak free form, 9b, and element 9a connects separator 23 and jet pipe 12, however element 9b connecting joint element 10;
-vertically pipe fitting 18 comprises that 18b, element 18a and 18b are connected respectively on joint component 19 and 17 with sleeve pipe and two nested each other element 18a of leak free form;
-vertical pipe fitting 9a, 9b by outer jointing jacket 37 around, this outer jointing jacket 37 is vertical rigidity, and the one side connects separator 23, and opposite side connecting joint element 10;
-outer jointing jacket 37 is free and pass separator 25 slidably;
-vertical pipe fitting 18a, 18b by outer jointing jacket 38 around, this outer jointing jacket 38 is vertical rigidity, and one side connecting joint element 19, and opposite side connecting joint element 17;
-outer jointing jacket 38 is free to slide with respect to midship mounting device 26; And
-laterally pipe fitting 14 by outer jointing jacket 39 around; this outer jointing jacket 39 is vertical rigidity; and one side connecting joint element 16; and opposite side connects pressurized heat air intlet 13; described outer jointing jacket 39 is equipped with the linkwork 40 of combination, and this linkwork 40 is arranged accordingly with this linkwork 27 and is connected.
In the embodiment variant of Fig. 7, outer jointing jacket 39 and linkwork 40 have been seen again.Difference with respect to the system of Fig. 6 is as follows:
-eliminated joint component 10 and 19;
-outer jointing jacket 37 and 38 is replaced by mono-outer jointing jacket 41, and this outer jointing jacket 41 is vertical rigidity, and side connection separator 23, and opposite side connecting joint element 17; And
-vertically pipe fitting 9 and 18 inner member 9a, 9b and 18a, 18b is replaced by mono-hot air direct internal element, this inner member comprises two part 42a nested each other and that can slide in the leak free mode toward each other, 42b, part 42a is connected on the nozzle 12, and part 42b is connected on the joint component 17.
In Fig. 8, shown the example of the system that is connected 43, this system comprise the ice removal system that is used for Fig. 6 and Fig. 7 in conjunction with linkwork 27 and 40.
In the system of being connected 43, linkwork 27 is identical with the mechanism of describing with reference to figure 5.About linkwork 40, it comprises two spherical couplings 44,45 that separate each other and be installed in the place, two ends of protecting sleeve section 46 respectively, and this protecting sleeve section 46 is inserted in the protecting sleeve 39 and surrounds pipe fitting section 30. Spherical coupling 44,45 is cooperated with the cylinder open pedestal 47,48 that is bound up on the described protecting sleeve 39 respectively.
To be readily appreciated that; by on internal protection cover 39, providing piecing devices 49 (for example type shown in the label 53 among Fig. 9) in the upstream and/or the downstream of linkwork 27 and 40; can make assembly 44; 45; 46 from cylindrical base 47; 48 throw off, thereby and for example arrive linkwork 27 for attended operation.
In Fig. 9, shown the modification 50 of connected system 43 of the combination of Fig. 8.In this modification 50, the linkwork 51 that is similar to linkwork 40 is inserted in the pipe fitting 14, and the linkwork 52 that is similar to linkwork 27 is inserted in the protecting sleeve 39 via at least one quick coupling 53.
In the modification 50 of connected system, linkwork 51 both can be easy to approaching, also can be easy to dismounting.
Claims (11)
1. give the system in particular for hollow leading edge (11) deicing of the air intake port cover (8) of the turbine engine (1) of aircraft for one kind, described ice removal system comprises:
-be suitable for the pressurized heat blast injection to described hollow leading edge (11) in-to-in nozzle (12);
-be installed on the hot-fluid producer (2) of described turbine engine (1), be used for extracting the device (13) of pressurized heat air;
-being used for from the hot air circulate pipeline (9,14,18) of described draw-out device (13) to the described pressurized heat air of described nozzle (12) conveying, described hot air circulate pipeline comprises the branch of two structures that meet at right angles, that is:
Transverse branch (14), its end are connected on the described draw-out device (13) rigidly, and
Vertical branch (9,18), it is laterad arranged with respect to described turbine engine (1) and its end is connected on the described nozzle (12), and
-be arranged in described nozzle (12) zone, be used for described vertical branch (9,18) is fastened to securing device (23) on the described air intake port cover (8),
It is characterized in that, leak free linkwork (27) is installed in wherein at least one described branch of described hot air circulate pipeline, be used to make described right-angle structure to be out of shape about described linkwork.
2. ice removal system according to claim 1 is characterized in that, described leak free linkwork (27) is the spherical coupling type.
3. ice removal system according to claim 2 is characterized in that, described leak free linkwork (27) comprises each other two spherical couplings (28,29) that connect and separate along the described branch of described hot air circulate pipeline.
4. according to each described ice removal system in the claim 1 to 3; it is characterized in that; each branch of the pivotally attached of described hot air circulate pipeline includes the hot air direct internal element (14) that is equipped with described leak free linkwork (27); and around the protecting sleeve outer member of described inner member (14); described outer member is equipped with the linkwork of combination, and the described leak free linkwork (27) of this linkwork and described inner member (14) is arranged accordingly and implemented.
5. ice removal system according to claim 4 is characterized in that, described protecting sleeve outer member is a detouchable.
6. ice removal system according to claim 5 is characterized in that, at least one in the linkwork (27) of described inner member (14) and the linkwork of described outer member is knock-down spherical coupling type.
7. ice removal system according to claim 6 is characterized in that, in having the linkwork of knock-down spherical coupling, described spherical coupling is cooperated with cylindrical surface.
8. according to each described ice removal system in the claim 1 to 7, it is characterized in that the described transverse branch of only hinged described hot air circulate pipeline.
9. according to each described ice removal system in claim 4 to 7 and the claim 8, it is characterized in that:
Described vertical branch of-described hot air circulate pipeline comprises hot air direct internal element and around the protecting sleeve outer member of described inner member;
An element in two composed components of-described vertical branch is vertical rigidity, and another element in the described composed component comprises at least two parts nested each other and that can slide relative to one another in the leak free mode;
Two composed components of-described vertical branch connect each other at its place, two ends;
-in described mentioned nozzle area, described two composed components are connected on the described securing device together rigidly; And
-in described transverse branch zone; on the one hand; the described hot air direct internal element of the described hot air direct internal element of described vertical branch and transverse branch connects each other; and on the other hand, the described protecting sleeve outer member of described vertical branch and the described protecting sleeve outer member of transverse branch connect equally each other.
10. according to each described ice removal system in claim 4 to 7 and the claim 8, it is characterized in that:
Vertical branch of-described hot air circulate pipeline comprises at least two sections of front and back phase ground connection installation each other;
-each described section comprises hot air direct internal element (9a, 9b; 18a is 18b) with around the protecting sleeve outer member (37,38) of described inner member;
An element in-each two composed component (37,38) of described section is vertical rigidity, and another element in the described composed component comprises at least two parts (9a, 9b nested each other and that can slide relative to one another in the leak free mode; 18a, 18b);
-each two composed component of described section connect each other at its place, two ends;
Two sections of-described vertical branch are engaged with each other, so that connect their composed component respectively;
-in described nozzle (12) zone, two composed components of one section in described two sections are connected to (23) on the described securing device together rigidly; And
-in described transverse branch zone; on the one hand; the described hot air direct internal element of described hot air direct internal element of another section of described section and described transverse branch connects each other; and on the other hand, the described protecting sleeve outer member of described another section and the protecting sleeve outer member of described transverse branch connect equally each other.
11., it is characterized in that described securing device comprises the separator (23) of the described hollow leading edge of sealing (11) according to each described ice removal system in the claim 1 to 10.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0602624A FR2898867B1 (en) | 2006-03-27 | 2006-03-27 | SYSTEM FOR DEFROSTING AN AIR INLET CAP FOR A TURBOMOTEUR. |
| FR0602624 | 2006-03-27 | ||
| PCT/FR2007/000483 WO2007110499A1 (en) | 2006-03-27 | 2007-03-22 | System for deicing an air inlet cowl for a turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101410299A true CN101410299A (en) | 2009-04-15 |
| CN101410299B CN101410299B (en) | 2014-10-15 |
Family
ID=37499471
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200780010760.9A Active CN101410299B (en) | 2006-03-27 | 2007-03-22 | System for deicing an air inlet cowl for a turbine engine |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US8047470B2 (en) |
| EP (1) | EP1999019B1 (en) |
| JP (1) | JP4934783B2 (en) |
| CN (1) | CN101410299B (en) |
| AT (1) | ATE467558T1 (en) |
| BR (1) | BRPI0706823A2 (en) |
| CA (1) | CA2641069C (en) |
| DE (1) | DE602007006450D1 (en) |
| FR (1) | FR2898867B1 (en) |
| RU (1) | RU2413081C2 (en) |
| WO (1) | WO2007110499A1 (en) |
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| CN105673983A (en) * | 2014-12-08 | 2016-06-15 | 空中客车运营简化股份公司 | Antifreeze system for a pipework |
| CN105756783A (en) * | 2016-04-21 | 2016-07-13 | 河南永新科技有限公司 | Gas turbine intake dustproof anti-icing device |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
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| US3396992A (en) * | 1966-12-15 | 1968-08-13 | Gen Connector Corp | Connector for hot fluid conduits |
| US4669757A (en) * | 1982-08-05 | 1987-06-02 | Bartholomew Donald D | High pressure fluid conduit assembly |
| AU581684B2 (en) * | 1984-10-08 | 1989-03-02 | Short Brothers Plc | Duct for hot air |
| DE3912926A1 (en) * | 1988-04-21 | 1989-11-02 | Fuji Heavy Ind Ltd | MOTOR CONTROL DEVICE FOR AN ELECTRICAL POWER STEERING DEVICE |
| US4893847A (en) * | 1988-07-05 | 1990-01-16 | Stainless Steel Products, Inc. | Bearing seal for universal ball joint |
| FR2639702B1 (en) * | 1988-11-25 | 1991-03-22 | Aerospatiale | WATERPROOF AND REMOVABLE CONNECTION DEVICE FOR TWO TUBES, PARTICULARLY FOR FUEL TRANSFER INSTALLATION |
| FR2771452B1 (en) * | 1997-11-21 | 2000-04-14 | Aerospatiale | DEFROSTING DEVICE FOR AIR INTAKE COVER OF REACTION ENGINE |
| KR200222734Y1 (en) * | 2000-10-11 | 2001-05-15 | 주식회사디엔브이 | Decoupler for automobile exhaust pipe |
| US6854486B2 (en) * | 2002-05-13 | 2005-02-15 | Eaton Corporation | Fluid line assembly |
| US6682102B1 (en) * | 2002-09-23 | 2004-01-27 | James C. Betz | Hose-in-hose coupler |
-
2006
- 2006-03-27 FR FR0602624A patent/FR2898867B1/en not_active Expired - Fee Related
-
2007
- 2007-03-22 WO PCT/FR2007/000483 patent/WO2007110499A1/en active Application Filing
- 2007-03-22 BR BRPI0706823-9A patent/BRPI0706823A2/en not_active IP Right Cessation
- 2007-03-22 CA CA2641069A patent/CA2641069C/en active Active
- 2007-03-22 US US12/280,104 patent/US8047470B2/en active Active
- 2007-03-22 DE DE602007006450T patent/DE602007006450D1/en active Active
- 2007-03-22 CN CN200780010760.9A patent/CN101410299B/en active Active
- 2007-03-22 AT AT07731172T patent/ATE467558T1/en not_active IP Right Cessation
- 2007-03-22 RU RU2008142426/11A patent/RU2413081C2/en not_active IP Right Cessation
- 2007-03-22 EP EP07731172A patent/EP1999019B1/en active Active
- 2007-03-22 JP JP2009502139A patent/JP4934783B2/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102190084A (en) * | 2010-03-18 | 2011-09-21 | 空中巴士运作简易股份有限公司 | De-icing system comprising detection means for detecting an air leak in the hot air supply |
| CN102190084B (en) * | 2010-03-18 | 2016-05-25 | 空中巴士运作简易股份有限公司 | Comprise the defroster of the equipment of revealing for detection of hot-air supply system place |
| CN105673983A (en) * | 2014-12-08 | 2016-06-15 | 空中客车运营简化股份公司 | Antifreeze system for a pipework |
| CN105673983B (en) * | 2014-12-08 | 2019-11-26 | 空中客车运营简化股份公司 | Anti-freeze system for pipeline |
| CN105756783A (en) * | 2016-04-21 | 2016-07-13 | 河南永新科技有限公司 | Gas turbine intake dustproof anti-icing device |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| ATE467558T1 (en) | 2010-05-15 |
| DE602007006450D1 (en) | 2010-06-24 |
| CA2641069C (en) | 2013-10-15 |
| US20090020647A1 (en) | 2009-01-22 |
| JP2009531595A (en) | 2009-09-03 |
| CA2641069A1 (en) | 2007-10-04 |
| EP1999019B1 (en) | 2010-05-12 |
| FR2898867A1 (en) | 2007-09-28 |
| JP4934783B2 (en) | 2012-05-16 |
| RU2413081C2 (en) | 2011-02-27 |
| BRPI0706823A2 (en) | 2011-04-05 |
| EP1999019A1 (en) | 2008-12-10 |
| CN101410299B (en) | 2014-10-15 |
| RU2008142426A (en) | 2010-05-10 |
| US8047470B2 (en) | 2011-11-01 |
| WO2007110499A1 (en) | 2007-10-04 |
| FR2898867B1 (en) | 2008-12-19 |
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